Gyroscope wheel speed modulator

ABSTRACT

A modulator for controlling the frequency of the power applied to a gyroscope to rotate the seismic mass (wheel) of the gyro so as to compensate for movement of the gyro case about the spin axis of the gyro is disclosed. The modulator includes a slow acting phase-locked loop that includes: a high frequency (e.g., 20 MHz) crystal controlled voltage controlled oscillator (VCXO); a divider for dividing the VCXO frequency down by several decades (e.g., six decades); a phase comparator for comparing the relatively low frequency output of the divider with a low frequency reference signal; a loop filter for filtering the output of the phase comparator so as to give the loop its desired dynamic response characteristic and bandwidth; and, a summing amplifier for summing the output of the phase comparator with a rate signal having a voltage level linearly related to the rate of movement of the gyro case about its spin axis. The rate signal is obtained from a second gyro mounted so as to sense movement about the spin axis of the gyro whose power frequency is being modulated. The power frequency control signal is derived from the output of the VCXO via a divider, which may form part of the divider of the slow acting phase-locked loop.

BACKGROUND OF THE INVENTION

This invention is directed to gyroscopes and, more particularly, tocontrol systems for controlling the rate of rotation of the spinningmass (wheel) of a gyroscope such that the spin rate remains constant ininertial space.

Gyroscopes are widely used in navigation and control systems to provideinformation about the rate of movement of a vehicle with which they areassociated about three orthogonal axes, normally referred to as the yaw,roll and pitch axes. Depending upon the accuracy required, gyros varyfrom relatively inexpensive uncomplicated mechanism to relativelyexpensive, complicated mechanisms. Regardless of their expense andcomplication, most presently available gyros include a spinning mass. Inorder for a gyro to provide accurate rate information, the rotationalspeed of the spinning mass (wheel) in inertial space must either beknown very accurately in time or, preferably, held very constant at aknown speed. In a typical gyro used in an aircraft inertial navigationsystem, for example, the gyro wheel forms the rotor of a synchronousmotor. More specifically, an AC source connected to field coils mountedin the gyro case sets up a rotating field which is followed by the gyrowheel. As a result, the gyro wheel rotates at the same speed as thespeed of movement of the rotating field. Stated another way, because arelative angular position between the rotor and the field is maintainedand because the field rotates, the rotor rotates at the same speed asthe field. Since the speed of the rotating field is relative to thefield coils, which are mounted in the gyro case, and since the rotatingfield speed is proportional to the frequency of the AC source, if thefrequency of the AC souce is maintained highly stable at a known value,the speed of the gyro wheel is maintained at a highly stable known valuein inertial space. This result, however, is only true if the gyro casedoes not rotate about its spin axis.

In inertial guidance and navigation systems that mount gyros on aplatform, gyro case rotation about the gyro's spin axis is preventedbecause the position of the platform remains fixed in inertial space.This solution, however, cannot be used in a strapdown gyro system. In astrapdown gyro system, the gyro cases are attached to the body of avehicle. As a result, the gyro spin axes are forced to follow themovements of the vehicle. Consequently, when the vehicle rotates aboutthe spin axis of a particular gyro, the speed of the rotating magneticfield of the gyro no longer remains constant with respect to inertialspace. Rather, the rotational motion of the vehicle about the spin axisof the gyro will either increase or decrease the speed of the magneticfield and, thus, the speed of the gyro wheel relative to inertial space.

Since vehicles move in a random fashion as a result of many externalconditions, strapdown gyros rotate about their spin axes in a randommanner. Because the movement is random, the static angular position andspeed relationships between the spin vector of the gyro wheel and therotating magnetic field vector vary in a random manner.

In the general case, the instantaneous magnitude of the spin vector of agyro wheel is the sum of: (1) the appropriate component of the vehicleangular rate relative to inertial space (i.e., the rotational movementof the vehicle about the spin axis of the gyro); (2) the speed of therotating field relative to the gyro case; and, (3) a varying factorwhich depends upon the inertia of the spinning mass and the "stiffness"of the motor (damping, etc.). The second term (relative speed of therotating field), which is by far the largest of the three terms, can bekept highly constant by controlling the frequency of the AC source thatcauses the gyro wheel to spin, as discussed above. While the first andthird term contributions to the instantaneous magnitude of the gyrowheel spin vector are substantially lower than the second term, they arehigh enough to create unacceptable erros in precision navigationsystems, such as requied on aircraft, if ignored. The first term(vehicle movement about the spin axis of the gyro) can be readilydetermined by mounting a second gyro such that it senses movement aboutthe spin axis of the first gyro. Contrariwise, the third term is ahighly dynamic term and its continuous measurement is extremelydifficult.

In the past, various proposals have been made to overcome or eliminatethe errors created by the first and third terms described above. Theseproposals can be grouped under two approaches. The first approachmaintains the frequency of the gyro motor supply power constant andmeasures the first and third terms at frequent intervals. The measureddata is then used to correct the rate data produced by the gyro. Thesecond approach varies the frequency of the gyro motor AC power supplyin such a way that the second term counteracts excatly the variations infield rotation speed caused by vehicle movements about the spin axis ofthe gyro. If this compensation is done correctly, the gyro wheel is notsubject to angular accelerations and decelerations about its spin axis.As a result, the dynamic effects which create the third term vanish. Insummary, the first approach measures the first and third terms andmodifies the gyro rate data accordingly; and, the second approachmodifies the wheel speed relative the gyro case whereby the resultingdata does not include errors caused by the first and third terms.

One proposal for implementing the first approach described abovecomprises mounting pins on the gyro wheel. The pins are used to inducepulses in a coil affixed to the gyro case. The time interval betweenpulses is measured and used to determine the time it takes for the wheelto make one complete revolution relative to the position of the coil,i.e., the measured time interval is used to determine wheel speed. Thesemeasurements are then used to form the basis for determining the thirdterm. The first term, to an adequate degree of accuracy, is obtainedfrom another gyro mounted so as to sense rotation about the spin axis ofthe gyro whose wheel induces pulses in the coil. The second term, ofcourse, is known.

The problem with the foregoing proposal is that it is difficult toimplement in practice. First, complex computations, which are timeconsuming, must be made. Second, it is very difficult if not impossibleto obtain relative wheel speed data, with sufficient resolution andaccuracy, and with a sufficiently small delay, at intervals which arefrequent enough to satisfy the computation requirements. Even ifobtainable, the circuitry necessary to obtain this information iscomplex and, therefore, expensive. In this regard, mounting more thanone pin about the circumference of the wheel and measuring the timeinterval between the consecutive pulses produced by a fixed coil so asto determine wheel speed based on measuring only a fraction ofrevolution cannot be done accurately enough. Such measurements cannot bemade accurately enough because the pins cannot be positioned accuratelyenough. As a result, only the time between pulses induced by the samepin can be used. However, measuring the time needed for a fullrevolution to occur cannot, in a practical way, be done such that thenecessary resolution is achieved. In this regard, in order to meetaccurate navigation requirements, revolution measurements must be takensuch that a resolution of one part in 800,000 or better is achieved. Atypical navigation gyro wheel makes 100 revolutions per second.Consequently, the measurement of a single revolution with a resolutionof one part in 800,000 requires an 80 MHz counter setup. An 80 MHzcounter requires corresponding very fast reading and reset circuitry andis complex and expensive. Furthermore, only an average value over a fullrevolution is obtained. While several counters, each started atdifferent, staggered times, could be used to produce wheel speedinformation that is recent enough, such an arrangement still producesonly an average value over a full revolution. Further, such anarrangement is expensive due to the inclusion of several counters andtheir related subsystems.

In view of the foregoing discussion, it will be readily appreciated thatprior art proposals to keep the frequency of the gyro power supplyconstant and measure data sufficient for the first and third terms to bedetermined are generally unsatisfactory. Not only is the equipmentneeded to make the required measurements difficult to design, suchequipment is substantially more expensive than desirable.

Prior proposals for implementing the second approach generally describedabove, i.e., modulating the frequency of the gyro motor AC power supplyin such a way that the second term counteracts exactly the variations infield rotational speed (in inertial space) about the gyro spin axiscaused by vehicle movements, have also been generally unsatisfactory. Inthis regard, one prior proposal for implementing the second approachincludes a phase-lock loop. A divider connected between the output ofthe phase-locked loop signal source and the phase comparator of thephase-locked loop has a modulus (division factor) that is controlled bythe angular rate signal derived from a gyro mounted so as to detectvehicular movement about the rotational axis of the gyro whose wheelspeed is being modulated. The division factor varies by a factor δ froma nominal value m.

A major problem with this implementation is that it is impossible, in apractical system, to obtain wheel speed values having sufficientresolution for them to be usable in a fast response phase-locked loop ofthis type. In this regard, wheel speed resolution is given by theequation 1/(m+δ). If it is assumed that the wheel rotates at 100revolutions per second (36,000°/sec) and that vehicle rates up to+10°/second must be compensated for, δ will be very small compared to m.As a result, wheel speed resolution is essentially equal to 1/m. Asnoted above, a resolution equal to one part in 800,000 or better must beobtained. Hence, m must be equal to 800,000 or more. As will be readilyunderstood by those familiar with phase-locked loops, the frequencylevel of the output of phase-locked loop signal source (such as avoltage controlled oscillator) must be equal to m (the divider value)times the frequency level of a reference signal for lock to be achieved.The reference signal is externally produced and is compared with thefrequency divided down signal produced by the loop signal source in aphase comparator. The result of the comparison is used to control thefrequency of the loop signal source so that the loop becomes locked. Atthe present time crystal controlled voltage controlled oscillatorsproduce signals that are stable up to the 20 MHz range. As will bereadily appreciated by those skilled in the art, the implementation ofvariable modulus counters above 20 MHz is very difficult. As a result,signal sources having frequency values above this range are generallyunusable. Now if the foregoing resolution requirement (one part in800,000) is applied and the 20 MHz limitation is met, the referencedfrequency must have a value of 25 Hz, or less (20 MHz/800,000=25 Hz).This resulting low referenced frequency value means that thephase-locked loop will be slow acting, unless some highly complex phasecomparator is used. The phase-locked loop is slow acting, of course,because the variable inputs of the phase comparator can only be updated25 times per second at most. The end result is that a loop with abandwidth well below 1 Hz must be used; otherwise, limit cycling,excessive VCXO modulation due to the reference frequency component ofthe control signal and other undesirable effects will occur. Because theloop filter bandwidth is below 1 Hz, this arrangement will only be ableto compensate accurately for vehicle rate signals whose frequency doesnot exceed a small fraction of a Hz. While this limitation may beacceptable in some environments, it is not acceptable in otherenvironments, such as an aircraft environment, where gyro case frequencycomponents of 5 to 20 Hz and above occur and must be compensated for. Inthis regard, it should be noted that above these frequencies, theinertia of the wheel will keep its speed in inertial space constantbecause the third term cancels out the first term. Hence, it isfrequencies below 5-20 Hz (down to about 1/10 Hz) that must becompensated for by modulating the wheel speed of the gyro. With thephysical limitations of practical systems noted above, such compensationcannot be accomplished using the foregoing implementation of the secondapproach.

In summary, implementations of neither of the proposed approachesdiscussed above is satisfactory. While the present invention fallsgenerally within the second approach described above, it implements thatapproach in a manner substantially different than the manner describedabove. As will be better understood from the following discussion, theinvention avoids the results of the latter implementation, whereby it isuseful in environments wherein gyro case frequency components liesubstantially beyond the passband of the loop filter of the phase lockloop.

It is an object of this invention to provide a gyro wheel speed controlsystem.

It is a further object of this invention to provide a gyroscope wheelspeed modulation system that compensates for rotational movement of thecase of the gyro around the spin axis of the gyro.

It is another object of this invention to provide a new and improvedgyroscope wheel speed modulator that modulates the frequency of the gyroAC power supply such that the rotational speed of the gyro field variesin a manner that exactly counteracts movement of the gyro case about itsspin axis.

SUMMARY OF THE INVENTION

In accordance with this invention, a gyroscope wheel speed modulator isprovided. The modulator controls the frequency of the AC power appliedto a gyroscope to rotate the seismic mass (wheel) of the gyro in amanner that compensates for movement of the gyro case about the spinaxis of the gyro. The preferred form of the invention includes a slowacting phase-locked loop. The slow acting phase-locked loop includes:high frequency signal source, such as a crystal controlled voltagecontrolled oscillator (VCXO), that has a very narrow frequency band;and, a fixed divider for dividing the output of the VCXO down by severaldecades. The relatively low frequency output of the divider is comparedwith a low frequency reference signal in a phase comparator. The outputof the phase comparator is connected to one input of a summer via a loopfilter which, together with the large amount of frequency division,gives the loop a slow response. The second input of the summer isconnected to receive a signal having a voltage level related to the spinaxis angular rate of movement of the case of the gyro whose powerfrequency is being controlled. Preferably, the angular rate signal isobtained from a second gyro having a sense axis positioned so as tosense movement about the spin axis of the controlled gyro. As a resultof this arrangement, i.e., the angular rate signal not being required topass through the loop filter and the frequency divider, angular ratesignals well in excess of the frequency limits set by the loop filterand frequency divider combined can be utilized to vary, on a short termbasis, the frequency of the VCXO signal over its narrow band. Since theloop is very slow acting (e.g., 1/300 Hz), the output of the VCXO is notrapidly washed out by the loop filter. The power frequency controlsignal is, of course, derived from the output of the VCXO. Either theVCXO output can be used directly (via a suitable divider) or the outputof a particular stage of the divider forming a part of the phase-lockedloop can be utilized, as desired.

In a preferred embodiment of the invention, the VCXO produces an outputover a limited range lying in the MHz band. The loop divider divides theMHz output down to the Hz band and the reference frequency lies in theHz band. Also, preferably, the loop bandwidth has a cutoff frequencysubstantially below one (1) Hz.

BRIEF DESCRIPTION OF THE DRAWINGS

The foregoing objects and many of the attendant advantages of thisinvention will become more readily appreciated as the same becomesbetter understood by reference to the following detailed descriptionwhen taken in conjunction with the accompanying drawings wherein:

FIG. 1 is a block diagram of a gyroscope system including wheel speedmodulators formed in accordance with the invention;

FIG. 2 is a generalized block diagram of a wheel speed modulator formedin accordance with the invention;

FIG. 3 is a detailed block diagram of a gyroscope wheel speed modulatorformed in accordance with the invention; and,

FIG. 4 is a series of waveforms utilized to describe the gyroscopewheel-speed modulator illustrated in FIG. 3.

DESCRIPTION OF THE PREFERRED EMBODIMENT

In order for the invention to be more readily understood, prior todescribing a preferred embodiment of a wheel speed modulator formed inaccordance with the invention, a description of a gyroscope system inwhich a wheel speed modulator formed in accordance with the invention isuseful is set forth. In this regard, attention is directed to FIG. 1.FIG. 1 illustrates first and second strapdown gyros 11 and 13. Bystrapdown, is meant that the cases of the gyros are affixed to thevehicle in which the gyroscopes are mounted. For purposes of discussiononly, the gyros are denoted as single-degree-of-freedom gyros with thesense axis of each gyro oriented so as to sense rotational movementabout the spin axis of the other gyro. In other words, the second gyro13 has its sense axis mounted so as to sense rotational movement aboutthe spin axis of the first gyro 11; and, the sense axis of the firstgyro 11 is mounted so as to sense rotational movement about the spinaxis of the second gyro 13. As will be readily appreciated by thoseskilled in that art and others, of course, each of the gyros could betwo-degree-of-freedom gyros, i.e., gyros that sense rotational movementabout two orthogonal (X-Y) axes. If so, one of the sensing axes of oneof the gyros will be mounted so as to sense movement about the spin axisof the other gyro and vice versa.

The gyroscope system illustrated in FIG. 1 also includes: first andsecond three-phase (3φ) generators 15 and 17; first and second gyrocontrol circuits 19 and 21; first and second wheel speed modulators 23and 25; and, a reference signal source 27.

The first three-phase generator 15 powers the first gyro 11 in aconventional manner with AC power. The frequency of the power producedby the first three-phase generator 15 is controlled by the first wheelspeed modulator 23. In addition, the first three-phase generatorreceives power from a suitable DC power source. Similarly, the secondthree-phase generator 17 receives power from a suitable DC power sourceand powers the second gyro 13. The frequency of the power produced bythe second three-phase generator is controlled by the second wheel speedmodulator 25.

The first control circuit 19 receives a signal from the pickoff coil ofthe first gyro 11 and, in accordance therewith, applies power to thecompensating torque coil of the first gyro 11. That is, when rotationalmovement occurs about the sense axis of the first gyro, such movementmodulates a pickoff coil signal. The modulated pickoff coil signal isamplified by a suitable pickoff amplifier and applied to the controlcircuit 19. The control circuit demodulates the pickoff coil signal and,in accordance therewith, via a power amplifier and other well-knownservo loop circuitry, controls the value of a torquer coil current thatis applied to the torquer coils of the first gyro 11. The torquer coilcurrent is adequate to maintain the seismic mass of the gyro in itsnormal position. The torquer coil current level is linearly related tothe rate of rotational movement and is applied to suitable downstreamcircuitry. Similarly, the second control circuit 21 receives a modulatedsignal from the pickoff coil of the second gyro 13 when rotationalmovement occurs about the sense axis of the second gyro and applies atorquer coil current to the torquer coils of the second gyro 13.

The signal applied to the torquer coils of the second gyro 13 is alsoapplied to the first wheel speed modulator 23. And, correspondingly, thesignal applied to the torquer coils of the first gyro 11 is applied tothe second wheel speed modulator 25. In addition, the first and secondwheel speed modulators receive a reference signal from the referencesignal source 27.

The reference signal source is a highly stable signal source. Thefrequency of the reference signal controls the speed of rotation of theseismic mass (wheel) of the gyros via the first and second wheel speedmodulators 23 and 25. As long as no rotation is sensed about the spinaxis of the gyros, the reference signal maintains the speed of rotationof the gyro wheels constant. When rotation about the spin axis of onegryo is sensed by the other gyro, the reference signal frequency ismodulated by the wheel speed modulator, i.e., the frequency is increasedor decreased by a slight amount. The frequency change exactlycompensates for the rotation of the case of the gyro about its spinaxis. In this manner, compensation is provided for rotational movementof the case about its spin axis, whereby the speed of rotation of thewheel of the gyro whose case is rotating remains fixed in inertialspace. More specifically, the frequency of the related three-phasegenerator signal is modulated in such a way that the speed of rotationof the gyro wheel relative to the case varies so as to exactlycounteract the variation in the rotation of the field (in inertialspace), about the gyro spin axis caused by vehicle movements.Consequently, the gyro wheel is not subject to angular accelerations anddecelerations about its spin axis, whereby the dynamic effects, whichcreate the third term (discussed above) of the series of terms thatdefine the instantaneous magnitude of the spin vector of the gyro wheel,are eliminated.

FIG. 2 is a generalized block diagram illustrating a wheel speedmodulator formed in accordance with the invention and comprises: acrystal controlled voltage controlled oscillator (VCXO) 31; first andsecond fixed modulus dividers 33a and 33b; a phase comparator 35; a lowpass loop filter 37; a summing amplifier 39; and, a noise filter 41. Aswill be readily appreciated by those skilled in the oscillator art, aVCXO is a high frequency (e.g., 20 MHz) oscillator whose frequency canbe varied slightly about a nominal frequency, i.e., the VCXO is a narrowband (+0.1% about a nominal value) oscillator.

The output of the VCXO is connected to the input of the first divider33a. The output of the first divider 33a is connected to the input ofthe second divider 33b and to the frequency control input to thethree-phase generator whose output power frequency is to be controlled.Obviously, these connections are exemplary. That is, the output of theVCXO 31 could be applied via one or more other dividers to the input ofthe three-phase generator and the two dividers 33a and 33b couldcomprise a single divider; or, a multitude of dividers. In this regard,in a practical embodiment of the invention, several physical dividersare necessary because the output of the VCXO is divided down by severaldecades. Preferably, a 20 MHz nominal VCXO signal is divided down to anominal 20 Hz signal by dividers having a combined division modulus of10⁶. In any event, the output of the second divider 33b is connected toone input of the phase comparator 35. The other input of the phasecomparator is connected to receive the reference frequency signal, whichis designated f_(REF). The output of the phase comparator 35 isconnected through the low pass loop filter 37 to one input of thesumming amplifier 39. The angular rate signal obtained from the othergyro is connected through the noise filter 41 to the second input of thesumming amplifier 39. The output of the summing amplifier 39 isconnected to the voltage control input of the VCXO 31.

It will be appreciated from the foregoing description that the controlvoltage applied to the VCXO is the sum of the low pass loop filtersignal and the angular rate signal derived from the other gyro, i.e.,the gyro having a sense axis positioned so as to sense movement aboutthe spin axis of the gyro whose power frequency is being controlled.

The low pass loop filter is formed such that the phase-locked loop is asecond order loop. Preferably, the loop passes only signalssubstantially below one (1) Hz. In fact, preferably, the cutofffrequency of the loop is around 1/300 Hz. In any event, the constants ofthe loop are dimensioned in such a way that the loop reacts very slowlyto changes in the output of the VCXO caused by the spin axis angularrate signal.

If the spin axis angular rate signal has been constant for an adequateperiod of time, the loop will be stable, whereby the frequency of theVCXO signal will have a value equal to the division factor (m) of thefirst and second dividers 33a and 33b times f_(REF), i.e., f_(VCXO)=mf_(REF). When the vehicle to which the case of the gyro is attachedrotates, the spin axis angular rate signal will modulate the frequencyof the VCXO signal. For relatively rapid changes in the spin axisangular rate signal, the slow acting loop will not have time to wash outthe effect of the spin axis angular rate signal on the frequency of theVCXO signal. If a VCXO having a linear control law is used (f_(VCXO=)KV_(c)), the output of the second divider 33a will vary in such a waythat a spin axis angular rate having a frequency level adequately abovethe passband of the low pass loop filter 37 will be cancelled. Assumingthat the gyro wheel speed is 100 revolutions per second or 36000° persecond, and that the angular rate is 10° per second, the modulation is±0.03% (10/36000=0.0003=0.03%), well within the ±0.1% availablefrequency band of a VCXO. (10°/sec=10 Hz angular rate signal.)

It should be noted that the fact that low frequency spin axis angularrates are not compensated does not present a problem because frequencycomponents below about 1/10 Hz do not impair navigational accuracy ifleft uncompensated. On the other hand spin axis angular rates aboveabout 1/10 Hz, which do effect navigational accuracy, are compensatedfor quite accurately. The frequency limit of the invention is actuallydetermined by the passband of the noise filter 41. This filter isrequired to keep high-frequency noise signals away from the VCXO input.Preferably, the cutoff frequency of this filter (which may comprise aseries of filters) is about 40 Hz. Alternatively, the noise filter canbe designed to reject particular components of the spin axis angularrate signal known to be produced by the gyro producing the spin axisangular rate signal, as hereinafter described with respect to FIG. 3. Inany event, spin axis angular rate changes above 40 Hz do not needcompensation because the inertia of the wheel makes rate compensationunnecessary above 40 Hz.

It will be appreciated that the invention relies on the fact that noappreciable DC component is present in the angular rate signals, becauseDC components are washed out by the phase-locked loop. In mostapplications, particularly aircraft applications, this assumption istrue because the vehicle (aircraft) never sustains an appreciableangular rate in the same direction over an appreciable length of time.In this regard, an appreciable angular rate would mean that a largeangular displacement of the vehicle has taken place. Even after arelatively long flight, the total angular displacement of an aircraft issmall, especially along the pitch and roll axes.

Because a phase-locked loop is used to stabilize the nominal frequencyof the VCXO, the invention provides a very accurate wheel speed controlsystem. The system operates over a wide temperature range withouttemperature compensation or regulation. Not only is the nominal wheelspeed accurate, the modulation of the nominal frequency of the VCXO isaccurate over the range of modulating signals where accuracy is needed.In this regard, a VCXO with a control law that is linear within ±2percent should be used. Further, because a slow-acting, phase-lockedloop is provided, it is important that the frequency source (VCXO) havegood inherent short-term frequency stability. If this condition is notmet, the loop will not keep up with changes induced by the frequencysource. Further, it is important that the frequency source be preventedfrom reaching values too far removed from its useful range. In thisregard, if such values are obtainable, the loop will become unlocked.Because the loop is very slow acting, a substantial period of time willelapse before a locked condition is re-achieved. These reasons dictatewhy a crystal controlled voltage controlled oscillator (VCXO), having afrequency band of ±0.1%, is preferred. Obviously, other frequencysources that meet these criteria can be used, if desired.

As will also be appreciated by those skilled in the art, a slow-acting,phase-locked loop allows considerable phase-signal differences to buildup at the input of the phase comparator before a transient, such as aspin axis angular rate signal is washed out. As a result, the circuitparameters (particularly the reference frequency) must be chosen suchthat the worst case transient cannot overload the phase comparator. Ifthis condition is not met, the loop will become unlocked and go into asearch mode. As a result, a relatively long period of time may elapsebefore accurate operation is restored.

FIG. 3 is a block diagram illustrating in more detail a preferredembodiment of a wheel speed modulator formed in accordance with theinvention. The gyroscope wheel modulator illustrated FIG. 3 comprises: aVCXO 51; first and second loop dividers 53a and 53b; a loop pulsesynchronizer 55; a phase comparator 57; a loop filter 59; a summingamplifier 61; a two-pole low pass filter 63; a differential amplifier65; a reference oscillator 67; first and second reference dividers 69aand 69b; a reference pulse synchronizer 71; and an initializationcircuit 73. The phase comparator 57 comprises: a ramp generator 75; and,a sample and hold amplifier 77. Preferably, the VCXO produces a signalhaving a nominal frequency of known value such as 19,660,800 Hz and thereference oscillator 67 produces a stable high-frequency signal having aknown value such as 10 MHz.

The output of the VCXO 51 is connected to the input of the first loopdivider 53a. Preferably the first loop divider (which may comprise aseries of divider stages) divides the nominal frequency of the VCXO19,660,800 Hz) by 8192. As a result, the frequency of the output of thefirst loop divider 53a (at the VCXO nominal frequency) is 2,400 Hz. Thissignal is applied to the three-phase generator and to the input of thesecond loop divider 53b.

Preferably, the second loop divider 53b has a division factor of 120,whereby the frequency of the output of the second loop divider 53b (atthe nominal frequency of the VCXO) is 20 Hz. This signal is applied toone input of the loop pulse synchronizer 55. The loop pulse synchronizer55 also receives a clock pulse chain derived from the referenceoscillator 67 in the manner hereinafter described. Preferably, thefrequency of the clock pulse chain is 10 KHz. As a result, the output ofthe loop pulse synchronizer is a pulse train of 50 microsecond pulseshaving a nominal 20 Hz repetition rate (each pulse occurs at the leadingedge of the 20 Hz input), as shown on the first line of FIG. 4. Thesepulses are applied to one input of the phase comparator 57. Morespecifically, the output of the loop pulse synchronizer 55 is applied tothe input of the ramp generator 75. The ramp generator 75 is controlledby these pulses such that a new ramp signal is started each time a 50microsecond pulse occurs, as denoted by the second line of FIG. 4. Theoutput of the ramp generator is connected to the signal input of thesample and hold amplifier 77.

The output of the reference oscillator 67 is connected through the firstand second reference dividers 69a and 69b to the reference pulsesynchronizer 71. The output of the first reference divider 69a is the 10KHz clock pulse train applied to the loop pulse synchronizer 55. Thissame pulse train is applied to the reference pulse synchronizer 71. Withrespect to particular division factors, assuming the referencedoscillator is producing a signal at 10 MHz, the first divider dividesthe output of reference oscillator by 1,000 to produce the 10 KHz clockpulse train. The second divider divides the 10 KHz signal by 500 so asto produce a 20 Hz output. As a result, the output of the second pulsesynchronizer 71 is a series of 50 microsecond pulses at a highlyaccurate 20 Hz rate. This pulse train forms the reference signal that isapplied to the phase comparator 57. More specifically, the output of thereference pulse synchronizer 71 is connected to the control input of thesample and hold amplifier 77.

The operation of the phase comparator is next described. The pulse chainproduced by the loop pulse synchronizer 55, as previously noted, causesa new ramp signal to start each time a pulse occurs. The sample and holdamplifier is commanded to sample by the 50 microsecond pulse outputs ofthe reference pulse synchronizer 71. In a conventional manner, thesample and hold amplifier samples its signal input during the 50microsecond pulse periods and holds each sample value until it is nextcommanded to sample. As long as the input is the same each time thesample and hold amplifier samples its signal input, its output remainsconstant.

Assuming first that the frequency of the pulse chain produced by thefirst pulse synchronizer 55 remains constant (which occurs when no casemovement about the spin axis is sensed), the sample and hold amplifierwill sample the ramp output of the ramp generator at a fixed point withrespect to the start of a ramp, each time the sample and hold amplifieris enabled by the output of the reference pulse synchronizer 71. Thisoutput is illustrated on the left side of FIG. 4. When the output of theVCXO changes in the manner hereinafter described, the pulse output ofthe loop pulse synchronizer will change position in time, as illustratedin an exemplary manner by the fifth pulse in the first line of FIG. 4.As a result, the next ramp starts at a different point in time. Becausethe pulses produced by the reference pulse synchronizer 71 are fixed intime, the sample and hold amplifier samples at a different point in theramp. Thus, the output of the sample and hold amplifier changes. Hence,a VCXO frequency change causes a change in the output of the sample andhold amplifier 77, which output represents the phase difference betweenthe phase comparator inputs.

The output of the sample and hold amplifier is combined with a DC offsetsignal, produced by a DC offset source 79. The combined signal isapplied through the loop filter 59 to one input of the summing amplifier61. The spin axis angular rate signal derived from the other gyroscopeis applied to the differential amplifier 65. The output of thedifferential amplifier is applied through the two-pole low pass filter63 to the second input of the summing amplifier 61. The output of thesumming amplifier 61 is applied to the voltage control input of the VCXO51.

In operation, a spin axis angular rate signal denoting movement aboutthe spin axis of the gyro whose wheel speed is being controlled causesthe frequency of the output of the VCXO to change. This change causes achange in the output of the sample-and-hold amplifier as previouslydescribed. The sample-and-hold amplifier change tends to cause theoutput of the VCXO to return to its nominal frequency. However, becausethe loop is slow acting, the VCXO does not return to its nominalfrequency via this route (i.e., the spin axis angular rate signal is notwashed out) prior to the spin axis angular rate signal ending (orchanging to a different value).

The output voltage of the sample and hold amplifier contains a very low20 Hz component. The use of a phase comparator with a low referencefrequency ripple content in its output is significant. Specifically, ifa comparator that required heavy filtering in the loop filter were usedbecause the phase comparator signal contained a very highreference-frequency ripple, excessive phase-shift would be introduced.Such phase-shift would destroy the effective operation of the invention.

The loop filter is dimensioned in such a way (taking other circuitparameters, particularly the division factors of the first and secondloop dividers 53a and 53b, into account) that a second order loop with a1/300 Hz cutoff frequency is provided. Preferably, the second order loophas a damping coefficient of 0.7 and, as noted, a cutoff frequency inthe order of 1/300 Hz or less. (It should be noted that a cutofffrequency below 1/1000 could produce unacceptable drift). The DC offsetis added to the phase comparator output in order to center its operatingrange about zero (it extends from -π to +π radians). The differentialamplifier eliminates common mode effects and the two-pole low passfilter eliminates noise. The two poles of the two-pole low pass filterare centered at multiples of the wheel spin frequency of the other gyroso as to eliminate noise which is known to occur at those frequencies.The initialization circuit 73, which is connected to all of thedividers, presets the dividers such that the correct phase-relationshipoccurs at the output of the comparator for a steady state condition(fixed angular rate input). As a result of the inclusion of aninitialization circuit, the loop does not have to go through a bigtransient at turn-on and the frequency of the VCXO signal is immedatelyclose to its nominal value. This allows the system to be useful as soonas the gyro wheel speed is up to its synchronous speed.

The loop parameters (especially the reference frequency) are chosen insuch a way that a worst-case transient rate signal cannot overload thephase-comparator. As a result, long unlocked time periods are eliminatedand linear operation is maintained. In this regard, the wheel speedmodulator parameters should comply with the following equation:

    360 K.sub.1 K.sub.2 K.sub.3 K.sub.4 =1

where:

K₁ = scaling of the spin axis angular rate signal in volts/°/sec;

K₂ total amplification of the spin axis angular rate signal between thesensing gyro and the input of the VCXO;

K₃ = relative change in the frequency of the VCXO output in terms ofinput voltage expressed in volts; and,

K₄ = number of revolutions per second of the gyro wheel. A suitable VCXOis the model CO-27IV sold by the Vectron Corporation, Norwalk, Conn.Such a VCXO, used in an actual embodiment of the invention, had: afrequency deviation of ±0.03%; linearity of 1% a frequency stabilitybetween 0° and 50° C. of ±0.001%.

It is pointed out that a mathematical analysis of a particular circuithas shown that the slowness of the loop is not due to the loop filterbut rather to the frequency division of the VCXO signal. In fact theloop filter amplifies 20 Hz components in the output of the sample andhold amplifier, rather than attenuating them. This result adds to theneed for a ripple-free phase-comparator. As will be readily understoodby those skilled in the art, many phase-comparators do not meet thisrequirement.

While a preferred embodiment of the invention has been illustrated anddescribed, it will be appreciated that various changes can be madetherein without departing from the spirit and scope of the invention.For example, a phase-comparator other than a phase comparator comprisinga ramp generator and a sample and hold amplifier can be utilized, ifdesired, as long as the phase comparator provides a generally ripplefree output. Moreover, various frequencies, other than thosespecifically denoted above can be utilized, as desired. In essence, theinvention requires a slow-acting phase-locked loop whose control signalis combined with a spin axis angular rate having a frequencysubstantially above the loop frequency immediately prior to the combinedcontrol signal being applied to a narrow band signal source. While theinvention has been described in conjunction with gyro systems, whichform the environment within which it was developed, it is to beunderstood that the invention may also find use in other environmentswherein a control signal having a frequency beyond the loop frequency isused to control the frequency of the loop signal source on a short termbasis. Consequently, the invention can be practiced otherwise than asspecifically described herein.

The embodiments of the invention in which an exclusive property orprivilege is claimed are defined as follows:
 1. A gyroscope wheel speedmodulator for producing a signal suitable for controlling the frequencyof the power applied to a gyro so as to compensate for movement of thegyro case about the spin axis of the gyro and, thereby, maintain thespin rate of the seismic mass of the gyro constant in inertial space,said gyroscope wheel speed modulator comprising:high frequencyoscillator means for producing a high frequency signal having afrequency value lying in a very narrow band about a nominal highfrequency; divider means connected to said high frequency oscillatormeans for dividing down the signal produced by said high frequencyoscillator means, said divider means producing first and second outputsignals, said first output signal being a low frequency signal lyingseveral decades below the frequency of the signal produced by said highfrequency oscillator means and said second output signal being anintermediate frequency signal having a frequency lying between thefrequency of the signal produced by said high frequency oscillator meansand the frequency of said first output signal, said intermediatefrequency signal suitable for controlling the frequency of power to beapplied to a gyro to rotate the seismic mass the gyro; reference signalmeans for producing a highly accurate and stable low frequency signal;phase comparator means connected to said divider means and to saidreference signal means for receiving said first output signal producedby said divider means and said highly accurate and stable low frequencysignal produced by said reference signal means, said phase comparatormeans comparing said first output signal produced by said divider meansand said highly accurate and stable low frequency signal produced bysaid reference signal means and producing, in accordance therewith, alow ripple output signal having a magnitude related to the phasedifference between said first output signal produced by said dividermeans and said highly accurate and stable low frequency signal producedby said reference signal means; loop filter means connected to saidphase comparator means for receiving the output of said phase comparatormeans; and, summing means having a first input connected to receive theoutput of said loop filter means and a second input adapted to receive aspin axis angular rate signal having a magnitude related to the rate ofmovement of the gyro case of the gyro whose power frequency is to becontrolled about the spin axis of said gyro, said summing means summingits input signals and producing an output signal in accordancetherewith, said output signal connected to said frequency oscillatormeans for controling the frequency of the signal produced by said highfrequency oscillator means.
 2. A gyroscope wheel speed modulator asclaimed in claim 1 wherein the high frequency oscillator signal is inthe MHz band.
 3. A gyroscope wheel speed modulator as claimed in claim 2wherein the frequency of the first output signal of said divider meansis in the Hz band.
 4. A gyroscope wheel speed modulator as claimed inclaim 3 wherein the highly accurate and stable low frequency signalproduced by said reference signal means is in the Hz band.
 5. Agyroscope wheel speed modulator as claimed in claim 4 wherein the cutofffrequency of said loop filter means and the division factor of thedivider means are such that a phase-locked loop having a bandwidthsubstantially below 1 Hz is formed.
 6. A gyroscope wheel speed modulatoras claimed in claim 1 wherein said high frequency oscillator means is acrystal controlled voltage controlled oscillator.
 7. A gyroscope wheelspeed modulator as claimed in claim 6 wherein the high frequencyoscillator signal is in the MHz band.
 8. A gyroscope wheel speedmodulator as claimed in claim 6 wherein the frequency of the firstoutput signal produced by said divider means when said high frequencyoscillator means is producing a signal at said nominal frequency isequal to the frequency of the highly accurate and stable low frequencysignal produced by said reference signal means.
 9. A gyroscope wheelspeed modulator as claimed in claim 8 wherein the frequency of the firstoutput signal produced by said divider means and the frequency of saidhighly accurate and stable low frequency signal are in the Hz band. 10.A gyroscope wheel speed modulator as claimed in claim 8 wherein saidhighly accurate and stable low frequency signal and said first signalproduced by said divider means are a series of short duration pulses.11. A gyroscope wheel speed modulator as claimed in claim 10 whereinsaid phase comparator means comprises:a ramp generator connected to thefirst output of said divider means for producing a series of rampsignals, each of said ramp signals being initiated upon the receipt ofone of the short duration pulses forming the first output signalproduced by said divider means; and, a sample and hold circuit havingits signal input connected to the output of said ramp generator and itssample command input connected to receive and be enabled by the seriesof short duration pulses forming said highly accurate and stable lowfrequency produced by said reference signal means, the output of saidsample and hold amplifier connected to the input of said loop filtermeans.
 12. A gyroscope wheel speed modulator as claimed in claim 11including low pass filter means for receiving said spin axis angularrate signal and filtering said spin axis angular rate signal prior tosaid spin axis angular rate signal being applied to said second input ofsaid summing means.
 13. A gyroscope wheel speed modulator as claimed inclaim 1 wherein the frequency of the first output signal produced bysaid divider means when said high frequency oscillator means isproducing a signal at said nominal frequency is equal to the frequencyof the highly accurate and stable low frequency signal produced by saidreference signal means.
 14. A gyroscope wheel speed modulator as claimedin claim 13 wherein the frequency of the first output signal produced bysaid divider means and the frequency of said highly accurate and stablelow frequency signal are in the Hz band.
 15. A gyroscope wheel speedmodulator as claimed in claim 1 wherein said highly accurate and stablelow frequency signal and said first signal produced by said dividermeans are a series of short duration pulses.
 16. A gyroscope wheel speedmodulator as claimed in claim 15 wherein said phase comparator meanscomprises:a ramp generator connected to the first output of said dividermeans for producing a series of ramp signals, each of said ramp signalsbeing initiated upon the receipt of one of the short duration pulsesforming the first output signal produced by said divider means; and, asample and hold circuit having its signal input connected to the outputof said ramp generator and its sample input connected to receive and beenabled by the series of short duration pulses forming said highlyaccurate and stable low frequency produced by said reference signalmeans, the output of said sample and hold amplifier connected to theinput of said loop filter means.
 17. In a gyroscope system including atleast two gyroscopes, one of said gyroscopes including a sense axispositioned so as to sense rotational movement about the spin axis of theother gyroscope and the other gyroscope including a sense axispositioned so as to sense rotational movement about the spin axis of thefirst gyroscope, the improvement comprising a gyroscope wheel speedmodulator associated with each of said gyroscopes for controlling thefrequency of the power applied to said gyroscopes so as to compensatefor movement of the cases of the gyroscopes about the spin axes of thegyroscopes and, thereby, maintain the spin rate of the seismic mass ofthe gyroscopes constant in inertial space, said gyroscope wheel speedmodulators each comprising:a high frequency oscillator means forproducing a high frequency signal having a frequency value lying in avery narrow band about a nominal high frequency; divider means connectedto said high frequency oscillator means for dividing down the signalproduced by said high frequency oscillator means, said divider meansproducing first and second output signals, said first output signalbeing a low frequency signal lying several decades below the frequencyof the signal produced by said high frequency oscillator means and saidsecond output signal being an intermediate frequency signal having afrequency lying between the frequency lying between the frequency of thesignal produced by said high frequency oscillator means and thefrequency of said first output signal, said intermediate frequencysignal connected to control the frequency of power applied to one ofsaid gyros, to rotate the seismic mass of that gyro; reference signalsmeans for producing a highly accurate and stable low frequency signal;phase comparator means connected to said divider means and to saidreference signal means for receiving said first output signal producedby said divider means and said highly accurate and stable low frequencysignal produced by said reference signal means, said phase comparatormeans comparing said first output signal produced by said divider meansand said highly accurate and stable low frequency produced by saidreference signal means and producing, in accordance therewith, a lowripple output signal having a magnitude related to the phase differencebetween said first output signal produced by said divider means and saidhighly accurate and stable low frequency signal produced by saidreference signal means; loop filter means connected to said phasecomparator means for receiving the output of said phase comparatormeans; and, summing means having a first input connected to receive theoutput of said loop filter means and a second input adapted to receive asignal from the other gyro having a magnitude related to the rate ofmovement of the gyro case of the gyro whose power frequency is to becontrolled about the spin axis of said gyro, said summing means summingits input signals and producing an output signal in accordancetherewith, said output signal connected to said frequency oscillatormeans for controlling the frequency of the signal produced by said highfrequency oscillator means.
 18. The improvement claimed in claim 17wherein:the high frequency oscillator signal is in the MHz band; thefrequency of the first output signal of said divider means is in the Hzband; and, the highly accurate and stable low frequency signal producedby said reference signal means is in the Hz band.
 19. The improvementclaimed in claim 18 wherein the cutoff frequency of said loop filtermeans the the division factor of the divider means are such that aphase-locked loop having a bandwidth substantially below 1 Hz is formed.20. The improvement claimed in claim 17 wherein said high frequencyoscillator means is a crystal controlled voltage controlled oscillator.21. The improvement claimed in claim 20 wherein:the high frequencyoscillator signal is in the MHz band; the frequency of the first outputsignal of said divider means is in the Hz band; and, the highly accurateand stable low frequency signal produced by said reference signal meansis in the Hz band.
 22. The improvement claimed in claim 17 wherein thefrequency of the first output signal produced by said divider means whensaid high frequency oscillator means is producing a signal at saidnominal frequency is equal to the frequency of the highly accurate andstable low frequency signal produced by said reference signal means. 23.The improvement claimed in claim 22 wherein the frequency of the firstoutput signal produced by said divider means and the frequency of saidhighly accurate and stable low frequency signal are in the Hz band. 24.The improvement claimed in claim 22 wherein said highly accurate andstable low frequency signal and said first signal produced by saiddivider means are a series of short duration pulses.
 25. The improvementclaimed in claim 24 wherein said phase comparator means comprises:a rampgenerator connected to the first output of said divider means forproducing a series of ramp signals, each of said ramp signals beinginitiated upon the receipt of one of the short duration forming thefirst output signal produced by said divider means; and, a sample andhold circuit having its signal input connected to the output of saidramp generator and its sample command input connected to receive and beenabled by the series of short duration pulses forming said highlyaccurate and stable low frequency produced by said reference signalmeans, the output of said sample and hold amplifier connected to theoutput of said loop filter means.